Standardfoliensatz-Englisch >1.04.2008

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Wasserstoff und Brennstoffzellen in der Luftfahrt

Deutsches Zentrum für Luft und RaumfahrtInstitut für Technische ThermodynamikPfaffenwaldring 38-48, D-70569 Stuttgart,

Josef KalloStuttgart, 23.10.2012

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Research Areas Space Flight German Space Agency Aeronautics Transport Research Energy Technology

DLR is the Aerospace Research Center as well as the Space Agency of the Federal Republic of Germany

Short Presentation DLR

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DLR - Sites and employees

7.000 employees working in 31 research institutes and facilities at 8 sites in 7 field offices.

Offices in Brussels, Paris and Washington.

Köln-Porz

Lampoldshausen

Stuttgart

Oberpfaffenhofen

Braunschweig

Göttingen

Berlin--Adlershof

Bonn

Trauen

Hamburg Neustrelitz

Weilheim

Berlin-Charlottenburg

Sankt Augustin

Darmstadt

-Ignition Prevention and Inerting

-Water Generation

-Supply of ElectricalNetwork

-Wing Anti Ice System

Higher Aircraft efficiency

Mission + safety improvements

-Air HumidificationSystem

-Multi Functional Fuel Cell System in Aircraft•Power provision •Emission free ground operation Autonomous Taxiing Maintenance bus supply Cargo reloading

•Electrical Main Engine Start

•EECS supply

•Water generation (potable water and water for toilets)

•Heat generation (icing prevention, hot water generation)

•Explosion and Fire Prevention and Suppression (inerting of tanks, cargo and e-bay compartment)

•Cockpit and / or Cabin air humidification

-Emission freeTaxi

-Electrical Main Engine Start and Water Injection

-EECS supply

Fuel Cell Aircraft and Airport Applications at the DLR

Airworthy technology development platform

- for emergengy power- for multifunctional use APU

- energy source for nose wheel drive

Modular architecture development platform

- for GPU applications- for high torque

applications (transport)

Modular airworthy propulsion platform

- for UAV applications- for general aviation

(up to 4 Pax or utility)

Fuel Cell Technology Transfer to Aircraft Application

Mechanical Strenght Simulation

Aircraft ApplicationFunctionality, Architecture, BOP

FC System from Transport Application

Airworthy technology development platform

- Fuel cell- DC/DC- hydrogen storage

Up to $6Bn investment in the past 15 years in the automotive industry

Vibration test for system qualification-Vibration test according to RTCA DO 160E Standard Vibration Fixed Wing

• Qualification H2-Tank pressurised with 350 bar (intank valve)

• Retested by manufacturer • Test succesfull

-Prequalification Development Platform• Equipped with componets• No significant mechanical failures detected

(Main component stack ok!)

Technology Transfer to Aircraft Application

System Voltage and Power before and after transfer to aircraft architecture

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No power loss by transfer to airworthy architecture

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Overview emission free taxi with fuel cell and e-NWD

Multifunctional fuel cell system in cargo bay

Fully integrated e-NWD

Motorelectronics

ControlBox and Data

Aquisition

High Torque 11.000Nm

Emission free system installation in A320

Fuel cell system and electrical nose wheel drive installationin cooperation with Airbus (Hamburg/Toulouse/Lutton) and Lufthansa Technik

A320 emission free taxi with fuel cell and e-NWD(1 July 2011)

Test DLR + Airbus + LHT

Zusammenfassung Sparpotenzial BZ + el. Antrieb (Bsp. FRA)Treibstoffverbrauch A320 + B737 konv. Treibstoffverbrauch A320 + B737 el. Antrieb

Einsparpotential für A320 + B737 ca. 44t Kerosin/Tag = 136t CO2/Tag Äquivalente benötigte Wasserstoffmenge ca. 2,4 t (332 Landungen, 334 Starts, 4.4.2009)

700 -1000h Triebwerkszeit-Einsparung

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Overview fuel savings and pollution minimization

DLR - Institut für Flugführung

Pollution minimization: conventional el. NWD with FC

Fuel savings:conventional el. NWD with FC

Savings up to 44 t kerosene/dayup to 136 CO2/daywith an aequivalent of 2,4 t H2

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Fuel Cell Aircraft and Airport Applications at the DLR

Airworthy technology development platform

- for emergengy power- for multifunctional use APU

- energy source for nose wheel drive

Modular architecture development platform

- for GPU applications

Modular airworthy propulsion platform

- for UAV applications- for general aviation

(up to 4 Pax or utility)

GPU- power spectrum on ground

Leistungsspektrum GPU

A 319 A 321

B 737 F 100

- Power range between 10 – 35 kWel.- Power slopes 60kW/40ms

B737

120ms

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Fuel cell – double layer capacitor

AnodeDR ,

AnodeDC ,

AnodeAdsR ,

AnodeAdsC ,

Ersatzschaltbild Elektrode Brennstoffzelle

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Fuel cell load characterisitcs

current from the doublelayer capacitor

backup for air buffer (30-100ms) small energy amount, high currents

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Overview „DLR - direct hybrid“

BZ/ICE

BZ/ICE (220-430V) Batt. (200-350V)

Batt

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Passiv controls self regulating system voltage spread

Very high dynamicsFuel cell – battery – direct hybrid10% 100% 10% load with2,5 Hz and power slope < 25ms

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Fuel Cell Aircraft and Airport Applications at the DLR

Airworthy technology development platform

- for emergengy power- for multifunctional use APU

- energy source for nose wheel drive

Modular architecture development platform

- for GPU applications- for high torque

applications (transport)

Modular airworthy propulsion platform

- for UAV applications- for general aviation

(up to 4 Pax or utility)

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High efficient airplane

Hydrogen storageFuel cell system

Antares DLR-H2 – overview, build-upTechnical Challenges:

- High efficient fuel cell system

- Optimized aeroelastics

- Minimized air drag

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Hydrogen storage Antares DLR H2

Hydrogen storage system intank valves (2x)

Hydrogen ISO Certified pressure storage system

(small system 1,8kg H2)(large system 4,6 kg H2)with intank valves up to 350 bar

Pressurized vibration proofed withRTCA DO160 fixed wing profiles

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LT - Next generation medium area fuel cell system (developed with Hydrogenics)

Air supply

Coolant

H2 supply

Cell Voltage Monitor + Controls

Sensors

Pressure regulator

Anode recirc

Weight Reduction from 12kW - 75kg to 35kW - 70 kg

System Efficiency (%LHV)

Base unit 80 -140 cells, metallic insulated connectors up to 360VMedium active area up to 12kW/35kW moduleTemp up to 80°C, overpressure up to 2,2 bar

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Fuel Cell Technology Antares DLR H2

Modular fuel cell system with cooling booster

Fuel Cell System Powerup to 33kW

modular system with high redundancy

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Optimized electrical network

> 40% overall efficiency (from chemical energy to movement)

Storage System

Energy Delivering System

High efficient power grid200-450V DC

Very high efficiency and reliability due to:- Direct coupling of the motor electronic to the fuel cell, without DC/DC

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Antares Flight on Hydrogen Fuel Cell

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Optimized electrical network

> 40% overall efficiency (from chemical energy to movement)

Storage System

Energy Delivering System

High efficient power grid200-450V DC at 40kW

Batteries

Very high efficiency and reliability due to:- Direct coupling of the motor electronic to the fuel cell/energy source, without DC/DC- High reliability due to direct, parallel use of an optional battery

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Hybridized Power FC + Batt

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Anwendungsforschung: Direkthybridisierung BZ Li-Ion

Direct Hybrid FC + Battery (Li Ion)Advantages:

- Power overboost for critical situations- Fuel cell in max. efficient mode- Very Low Cost Components!

Direct coupling FC + BattBattery shut down

Input für Batterieforschung in den Bereichen:- Sicherheit (Überspannung)- Zyklierbarkeit (Lebensdauer)- Thermomanagement - Effizienz (Batterie Management System) Hybridisiertes System mit 12kWh Li-Ion

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Lärm Emissionen Kolbenmotor vs. Brennstoffzellenantrieb

Cessna 152 Motorstart Antares DLR H2 Start und Flug

Folie 36Vortrag > Autor > Dokumentname > Datum

“Lärmbelastung” des DLR MotorseglersMessung in Anlehnung an ICAO Annex 16 Vol.1in 1000m Flughöhe kein messbarer Unterschied zu Hintergrundgeräuschen (Blätterrauschen, Wind)

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19:31:35 19:31:44 19:31:52 19:32:01 19:32:10 19:32:18 19:32:27 19:32:36 19:32:44 19:32:53

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Umgebung2. Überflug 1000m mit MotorMin SPL [dB(A)]Max SPL [dB(A)]

Antares direkt über der Messstelle

www.DLR.de • Folie 37 > Integrationsarbeiten > Dipl.-Ing. P. Rathke • Integration_BZ_Kamera.ppt > 15. Mai 2012

Integration - Kamerasystem + Wasserstoffantrieb

www.DLR.de • Folie 40 > Integrationsarbeiten > Dipl.-Ing. P. Rathke • Integration_BZ_Kamera.ppt > 15. Mai 2012

Bodenstation

Folie 41Vortrag > Autor > Dokumentname > Datum

Echtzeit-Orthorektifizierung der Luftbilder (2)

Positionierung bis max. 8cm

Folie 44Vortrag > Autor > Dokumentname > Datum

Verkehrsdatenerfassung im Projekt VABENE

Verkehrsdatenerfassung aus optischen Luftbildern

Automatische Detektion und Verfolgung von FahrzeugenDatenverarbeitung inklusive Senden zur Bodenstation in Echtzeit

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September 2012: Antares DLR H2 geht auf Langstreckenflug

- Start der Tour in Zweibrücken- Zwischenlandung in Hof- Teilnahme an der ILA mit An- und Abflug in

Berlin- Zwischenstopp in Hof- Endpunkt der Tour in Stuttgart am 20.09

Gesamtstrecke ca. 1500kmGesamtflugzeit ca. 15 Stunden mit An- und

Abflugphase

> Antares DLR H3 • 02. April 2012

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Vielen Dank für die Aufmerksamkeit !